| タイトル | Preliminary Base Pressures Obtained from the X-15 Airplane at Mach Numbers from 1.1 to 3.2 |
| 本文（外部サイト） | http://hdl.handle.net/2060/19980227195 |
| 著者（英） | Saltzman, Edwin J. |
| 著者所属（英） | NASA Dryden Flight Research Center |
| 発行日 | 1961-08-01 |
| 言語 | eng |
| 内容記述 | Base pressure measurements have been made on the fuselage, 10 deg.-wedge vertical fin, and side fairing of the X-15 airplane. Data are presented for Mach numbers between 1.1 and 3.2 for both powered and unpowered flight. Comparisons are made with data from small-scale-model tests, semiempirical estimates, and theory. The results of this preliminary study show that operation of the interim rocket engines (propellant flow rate approximately 70 lb/sec) reduces the base drag of the X-15 by 25 to 35 percent throughout the test Mach number range. Values of base drag coefficient for the side fairing and fuselage obtained from X-15 wind-tunnel models were adequate for predicting the overall full-scale performance of the test airplane. The leading-edge sweep of the upper movable vertical fin was not an important factor affecting the fin base pressure. The power-off base pressure coefficients of the upper movable vertical fin (a 10 deg. wedge with chord-to-thickness ratio of 5.5 and semispan-to-thickness ratio of 3.2) are in general agreement with the small-scale blunt-trailing-edge-wing data of several investigators and with two-dimensional theory. |
| NASA分類 | Aerodynamics |
| レポートNO | NASA-TN-D-1056
H-215 |
| 権利 | No Copyright |
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